CN103868994B - For detecting the detection device of the shock on composite structure and detection method - Google Patents
For detecting the detection device of the shock on composite structure and detection method Download PDFInfo
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- CN103868994B CN103868994B CN201310700773.6A CN201310700773A CN103868994B CN 103868994 B CN103868994 B CN 103868994B CN 201310700773 A CN201310700773 A CN 201310700773A CN 103868994 B CN103868994 B CN 103868994B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/045—Analysing solids by imparting shocks to the workpiece and detecting the vibrations or the acoustic waves caused by the shocks
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/22—Details, e.g. general constructional or apparatus details
- G01N29/24—Probes
- G01N29/2475—Embedded probes, i.e. probes incorporated in objects to be inspected
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/22—Details, e.g. general constructional or apparatus details
- G01N29/24—Probes
- G01N29/2481—Wireless probes, e.g. with transponders or radio links
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/023—Solids
- G01N2291/0231—Composite or layered materials
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/26—Scanned objects
- G01N2291/269—Various geometry objects
- G01N2291/2694—Wings or other aircraft parts
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- Acoustics & Sound (AREA)
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- Geophysics And Detection Of Objects (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
Abstract
Subject of the present invention is for detecting the detection device (10) of the shock on composite structure (12).The detection device (10) includes being used at least two acoustic modules (14 fixed to the composite structure (12), 14 1,14 2,3) and can be with each acoustic module (14 14,14 1, the processing unit (30) of 14 2,14 3) telecommunications.Advantageously, (14,14 1,14 2,14 is 3) independent on electric power and include the recording device of the respective sound wave sensed for record by its acoustic sensor (16) for each acoustic module.The invention further relates to a kind of airframes (12) of the composite structural part (40) of the detection device (10) including equipped with shock.Also, the invention further relates to the detection methods for detection equipped with the shock on the composite material aircraft device structure member (40) of the detection device (10) of shock.
Description
Technical field
The present invention relates to for detecting the detection device of the shock on composite structure and detection method.
Background technology
Composite material is widely used for aeronautics, the component including being used to manufacture the primary structure for forming aircraft fuselage.
Awing or when aircraft is stopped, these outer structural elements are easy to be subjected to various collisions.
Therefore, it is necessary to routinely, preferably these outer structural elements are examined before each new use of aircraft
It looks into.
This check damages to carry out by the way that searching is any caused by the collision on these structure members.
Since this check needs to carry out on all these components, so the time is long and makes one bored.
Moreover, it carries out the visual inspection of these structure members and is insufficient to.
In fact, the possible inside of the composite structure being collided is damaged, for example, by layering, present simultaneously
Go out the appearance similar to intact structure.
Therefore, there are in the case of damage suspicion, usually periodically carried out for the integrality of outer structural element
Ultrasonic examination, such routine inspection allow to detect the damage on the inside of composite structure.
According to first shortcoming, this conventional ultrasonic examination is still time-consuming and irksome operation, and transmitting is visited
Pin needs move in all outer structural elements to be checked.
Moreover, some regions of these outer structural elements are difficult to close to therefore, it is difficult to check.
According to another shortcoming, for the Impact energy of some grades, these conventional nondestructive inspections are used
Device does not still see accidental layering.
Therefore, in the design process of these outer structural elements, synusia is added in composite structure, to deposit
Ensure its restorability in the case of use conventional non-destructive testing apparatus that cannot detect the defects of.
These additional synusia add the overall weight of aircraft and are unfavorable for its performance.
Therefore, it is necessary to such a device and non-destructive methods, enabling identify and position in composite structure
Shock, and can determine the energy grade of shock to assess its degree of danger.
Therefore, from patent FR-2,937,953 for detecting and analyzing aircraft it is recognized that stop what opportunity experienced
The device of damage.
More specifically, this device is used for monitoring the door for the inner space for leading to aircraft or the opening of hatch.
For this purpose, the device includes：
- one row's piezo-type sensor is installed around the opening on the inner surface of fuselage, can sensed around described
The mechanical oscillation propagated in the airframe structure of opening can simultaneously generate the electric signal for the mechanical oscillation for representing to sense；
- processing unit is electrically connected to the row piezo-type sensor, it can be ensured that generated by sensor by conducting wire
Electric signal record, and to these electric signals carry out digital processing, with detect around the opening fuselage on shock simultaneously
It determines whether the shock has destructiveness, if with destructiveness, the shock will be positioned；
- around Local Alarm's device of door arrangement, the processing unit is electrically connected to by conducting wire and is hit described
Started when hitting with destructiveness by the processing unit；
- data concentrator is electrically connected to the processing unit by conducting wire, and the concentrator can be collected from described
The data with alert of processing unit simultaneously passes through conducting wire these data is electrically communicated to concentration indicator；
- concentration indicator is electrically connected to the data concentrator by conducting wire, can show the alarm shape of any opening
State, if detecting destructive shock, display and the relevant item of information in position hit.
Usually, document FR-2, the device described in 937,953 are not suitable for detecting the shock on composite structure, because
Metallic plate aircraft fuselage is developed for for this device.
Moreover, document FR-2, the device disclosed in 937,953 is only used for being located at when ground is stopped in aircraft and start.Cause
This, which cannot detect the shock in outer structural element in aircraft.
In addition, in document FR-2, device disclosed in 937,953, it is single that piezo-type sensor is wired to processing
Member, and processing unit is connected to data concentrator self by conducting wire, data concentrator is wired to mounted on driving
Concentration indicator in cabin.
Therefore, entire detection device must its design and assembling on be correctly joined to aircraft, thus if regardless of
It solves multiple components and a few hours labour is provided, this device cannot be used on existing aircraft.
The content of the invention
Therefore, it is an object of the invention to cut down prior art the shortcomings that.
For this purpose, the present invention provides a kind of detection device for being used to detect the shock on composite structure, the detection device
Including be used for be fixed to the composite structure at least two acoustic modules and can be long-range with each acoustic module
The processing unit of communication.
According to the present invention, each acoustic module includes acoustic sensor, electric energy generation device, passes through its acoustics for recording
Sensor sensing to sound wave recording device and be configured to the remote communication devices to communicate with the processing unit.
Due to the remote communication devices of acoustic module, the processing unit in aircraft need not be provided, flown in aircraft
The sound wave that row records in the process can remotely be recycled by the processing unit, thus be conducive to aircraft examination and maintenance behaviour
Make.
Further, since detection device, is just attached to by the independence of acoustic module completely without from its design and assembling
Aircraft, therefore be conducive to detection device and be attached to existing aircraft.
Preferably, the electric energy generation device of each acoustic module includes miniature kinetic energy generator.
For the implementation of detection device, being referred to as at least one acoustic module of primary module includes clock.
Moreover, still for the implementation of detection device, the remote communication devices of main acoustic module are configured to and the detection
Other acoustic modules communication of device.
The present invention also provides a kind of airframe, including equipped with the composite structure portion for hitting detection device
Part.
The acoustic module can be fixed on the surface of structure member and/or be arranged in structure member.
More specifically, when structure member mainly extends along a dimension, the detection device includes being fixed to the knot
Second acoustic module of the first acoustic module of the first end of structure component and the second end fixed to the structure member.
However, when the structure member mainly extends along two dimensions, the detection device includes being fixed to the knot
At least three acoustic modules of structure component, by least three acoustic mode acoustic module in the block separate two-by-two away from
From being all different.
Finally, the present invention also provides a kind of detection sides detected equipped with the shock on the structure member for hitting detection device
Method.
The detection method implements the detection device according to following step：
- by the communicator of main acoustic module to other acoustic module radiated radio frequency signals of detection device,
The radio frequency signals include the when base that this group of acoustic module of the detection device shares；
- propagated by the recording device records of each acoustic module in the definite duration through the structure member
Sound wave；
- sound wave recorded by each acoustic module is transferred to processing unit；And
- the sound wave that is passed of analysis is to detect any shock being happened on the structure member.
Advantageously, what the step of analyzing the sound wave being passed allowed to that assessment is happened on the structure member any hits
The degree of danger and/or positioning hit are happened at the shock on the structure member.
Different from the device of the prior art, detection device according to the present invention can be real in the flight course of aircraft
It applies.
Description of the drawings
Other feature and advantage will be showed by description below in conjunction with the accompanying drawings of the invention, the description only conduct
Example provides, in figure：
Fig. 1 is to show the portion according to the present invention equipped with the long linear structure component of composite material for hitting detection device
Divide perspective view；
Fig. 2 is the generalized schematic for the acoustic module for showing shock detection device according to the present invention；And
Fig. 3 is to show the portion according to the present invention equipped with the composite material pancake structure member for hitting detection device
Divide perspective view.
Specific embodiment
As shown in fig. 1, the present invention relates to for detecting the detection device 10 of the shock on composite structure 12.
Detection device 10 includes being used at least two acoustic modules 14 being fixed on composite structure 12 and can be with
The processing unit 30 of 14 telecommunication of each acoustic module.
As schematically illustrated in Figure 2, each acoustic module 14 includes acoustic sensor 16.
Therefore, each acoustic module 14 can sense as produced by the shock in structure 12 and be propagated in the structure 12
Sound wave, particularly Dirac types.
In the first deformation, acoustic sensor 16 is piezo-type sensor.
In second of deformation, acoustic sensor 16 is electromagnetic type sensor and including the helical for example with centring magnet
Pipe.
According to the present invention, each acoustic module 14 is independent on electric power.
It therefore, because need not be between acoustic module 14 or in another portion of acoustic module 14 and detection device 10
Between part conducting wire is set to connect, detection device 10 is attached to existing composite structure 12 it is possible that imagining, such as is tied
Close the composite structural part of the aircraft used.
In order to independent on electric power, each acoustic module 14 includes electric energy generation device 18.
Preferably, the electric energy generation device 18 of acoustic module 14 includes miniature kinetic energy generator 20.
Particularly structure 12 belong to aircraft and aircraft awing when, miniature kinetic energy generator 20 for example may
It is produced electricl energy based on the vibration caused by structure 12.
Certainly, electric energy generation device 18 further includes to store the electric power storage of the electric energy generated by miniature kinetic energy generator 20
Device 22.
Advantageously, each acoustic module 14 is made using the CMOS technology of low energy consumption.
Also, the record that each acoustic module 14 includes recording the sound wave sensed by its acoustic sensor 16 fills
Put 24.
Therefore, each acoustic module 14 can be recorded on the record period of definite duration through composite material knot
The sound wave that structure 12 is propagated, such as the sound wave propagated in aircraft by the composite structural part of aircraft.
Advantageously, these recording devices 24 use resettable memory.
Therefore, beginning of the recording device 24 in each new record cycle for example provides most before the taking off each time of aircraft
Big recording capacity.
For the operation of detection device, each acoustic module 14 includes being configured to communicate with processing unit 30 long-range logical
T unit 26.
These remote communication devices 26 are preferably using the form of the radio frequency transceiver 28 to work at high frequencies.
These remote communication devices 26 allow each acoustic module 14 of detection device 10 to communicate with processing unit 30, and
These acoustic modules 14 is allowed to be in communication with each other with its synchronous operation.
In fact, these remote communication devices 26 may be in record period to the output of processing unit 30 and each acoustic mode
The relevant data of sound wave that block 14 is recorded, for example, with during aircraft in the composite structural part of aircraft
The sound wave of record is related.
Therefore, as shown in fig. 1, processing unit 30 is independent, moveable.
Preferably, the communication between processing unit 30 and each acoustic module 14 is connected to processing list by means of conducting wire
The radio frequency reader 32 of member 30 carries out.
In fact, although processing unit 30 is moveable, radio frequency line is moved about in each acoustic module 14
Rate reader 32 is easier.
By means of radio frequency signals 36, which may remotely retrieve from composite structure 12 with remembering
The relevant data of sound wave recorded in the record cycle by each acoustic module 14.
In the case of the composite structural part of aircraft, between processing unit 30 and acoustic module 14, more typically
Be the telecommunication in detection device 10, may from the external recycling of aircraft in flight course by each acoustic mode
The relevant data of sound wave that block 14 is recorded.
Therefore, in the present invention, only acoustic module 14 is invariably present in composite structure 12 to be detected, i.e.
In the structure for imagining the aircraft used.
Finally, at least one acoustic module 14-1 of detection device 10 is referred to as main acoustic module, including clock 38.
The clock 38 is used for each acoustic module 14 fixed to composite structure 12 and is operated in its record period
Synchronization, i.e. for being fixed to these modules of same aircraft composite structural part in the flight course of aircraft
Operational synchronization.
In order to carry out the synchronization, the remote communication devices 26 of main acoustic module 14-1 be configured to detection device 10 its
Its acoustic module 14-2,14-3 communicates.
More specifically, main acoustic module 14-1 is sent by means of its remote communication devices 26 to other modules 14-2,14-3
Radio frequency signals 34, which includes the when base that all these module 14-1,14-2,14-3 are shared, in Fig. 1 and Fig. 3
It is shown.
The transmission of synchronizing signal 34 predictive of record period beginning, for example, in the departure time of aircraft.
Advantageously, can continue for verifying the signal synchronous with correction module 14-1,14-2,14-3's in record period
On time, i.e. for example the aircraft including the composite structural part equipped with detection device 10 flight it is lasting when
Between on, sent with the frequency that is determined by main acoustic module 14-1.
As shown in figures 1 and 3, the invention further relates to airframe 12, which is included equipped with shock
The composite structural part 40 of detection device 10.
In the first deformation arrangement of module shown in Fig. 1, two acoustic modules 14-1,14-2 are fixed to structural portion
On the surface 42 of part.
Preferably, the acoustic module 14 of detection device 10 is secured by gluing on structure member 40.
Alternatively, acoustic module 14 can be fixed to structure member 40 by any mechanical connection, which allows
Quickly connect and acoustic sensor 16 is allowed suitably to sense the sound wave propagated in structure member 40.
The first deformation arrangement of module 14 allows detection device 10 on the aircraft used.
In second of deformation arrangement of module shown in Fig. 3, three acoustic modules 14-1,14-2,14-3 are arranged on knot
In structure component 40, for example, being attached to the structure member 40 in the fabrication process.
This second deformation may realize the independent operation of module 14.
Second of deformation arrangement of module 14 is not to be necessarily required to combine detection device 10 in its design and period of assembly
To aircraft.
Actually, it is only necessary to replace the structural portion of existing aircraft 12 using the structure member 40 of implantation acoustic module 14
Part is attached to these components being present in aircraft without any wired connection.
Present invention additionally comprises the third deformation for combining the arrangement provided during the first is deformed with second above, wherein extremely
A few acoustic module 14 is fixed to the surface 42 of structure member 40, and at least one acoustic module 14 is arranged on structure member
In 40.
The present invention provides the different of detection device 10 also according to the design of structure member 40 and implements.
As shown in fig. 1, when structure member 40 mainly extends along a dimension D1, detection device 10 only includes being fixed to
The second acoustics of first acoustic module 14-1 of the first end 44 of structure member 40 and the second end 46 fixed to structure member 40
Module 14-2.
In fact, in the case of linear structural members 40, i.e., extend along single dimension D1, two acoustic module 14-
1st, 14-2 is enough to allow detection, positioning and the assessment to shock.
However, as shown in Figure 3, when structure member 40 mainly extends along two dimensions D2, D3, detection device 10 includes
At least three acoustic module 14-1,14-2,14-3 fixed to structure member 40 separate at least three acoustic modules 14-1,14-
2nd, distance L1, L2, L3 of acoustic module are different two-by-two in 14-3.
Different distance L1, L2 and L3 is necessary, so as to for example in the flight course of aircraft on structure member 40
When hitting, simultaneously led to by the association in time of the sound wave recorded by any of three modules 14-1,14-2,14-3
It crosses triangulation and is hit to position.
Certainly, present invention additionally comprises detection device 10 substantially along the reality in the structure member 40 of similar three dimensions extension
It applies or the acoustic module 14 of wherein three or more is fixed to implementation in structure member 40, regardless of whether what it mainly extended
The number of dimension.
Finally, present invention additionally comprises for detecting the detection method of the shock on composite material aircraft device structure member 40.
The detection method detects the shock being happened on structure member 40 including examinations device 10, is particularly navigating
During the flight of pocket.
The detection method is also possible to examinations device 10 to be located in the shock detected on structure member 40.
Also, the detection method also examinations device 10 detects the dangerous journey of shock to assess on structure member 40
Degree.
The detection of the shock being now incorporated on composite material aircraft device structure member 40 describes inspection according to the present invention
Survey method.
The step of before this method is implemented, is included in structure member 40 to be monitored and/or is implanted on structure member 40
The acoustic module 14 of detection device 10, as previously described.
Then, before detection device is used, such as hammer (acoustic hammer) into shape by means of sound and carry out calibrating acoustic module
14。
The calibration includes being directed at least one shock measured and demarcated on structure member 40 to measure by each sound
Learn the energy grade for the sound wave that module 14 is received.
It is then possible to know position of each acoustic module 14 compared with rum point, which may establish mathematical relationship
Formula provides position and the energy grade of random shock according to the sound wave sensed by each acoustic module 14.
After the calibration, it is ready to use detection device 10.
In the application mainly imagined in the present invention, the acoustic module 14 of detection device 10 is used to be recorded in flying for aircraft
The sound wave propagated in the duration of row order section through structure member 40.
Certainly, the present invention is not limited to this application, detection device may be also used in aircraft stop or on the ground
When mobile.
Before each the new cycle for the sound wave propagated by structure member 40 is recorded, the acoustics of device 10 is detected
The synchronization of module 14.
The synchronization via main acoustic module 14-1 other acoustic module 14-2 from communicator 26 to detection device 10,
14-3 radiated radio frequencies signal 34 carries out, what this group of acoustic module that radio frequency signals 34 include device 10 shared
Shi Ji.
Awing, this method is recorded in for example by the recording device 24 of each acoustic module 14-1,14-2,14-3
The sound wave propagated in the definite duration through structure member 40 is waited during flight.
After landing, this method will be recorded by communicator 26 by each acoustic module 14-1,14-2 and 14-3
Sound wave be transferred to processing unit 30.
Therefore, be processed unit 30 with the relevant data of sound wave by the propagation of structure member 40 during aircraft
It withdraws, is preferably withdrawn by radio frequency reader 32.
Then, this method analyzes the sound wave of transmission, with detection be awing happened on structure member 40 can
The shock of energy.
Pass through the sound wave (frequency spectrum, amplitude levels etc.) that acoustic module 14 is recorded and transferred and the formula obtained by calibration
Different analyses, may for example by comparison threshold value come assess the degree of danger for the shock being happened on structure member 40 and/or
Such as in order to which suitable equipment progress toposcopy is used to position the shock being happened on structure member 40.
Claims (13)
1. for detecting the detection device (10) of the shock on composite structure (12), which is characterized in that the detection device
(10) include be used for fixed to the composite structure (12) at least two acoustic modules (14,14-1,14-2,14-3) and
Can with the processing unit (30) of each acoustic module (14,14-1,14-2,14-3) telecommunication, each acoustic module (14,
14-1,14-2,14-3) include acoustic sensor (16), electric energy generation device (18), for record by its acoustic sensor (16)
The recording device (24) of the sound wave sensed and it is configured to the remote communication devices to communicate with the processing unit (30)
(26), wherein, the electric energy generation device (18) of the acoustic module (14,14-1,14-2,14-3) is sent out including miniature kinetic energy
Motor (20) and electric storage means (22), the miniature kinetic energy generator (20) are used to be based on vibrating as caused by structure and generating electricity
Can, the electric energy that the electric storage means (22) is generated for storage by the miniature kinetic energy generator (20).
2. it is according to claim 1 for detecting the detection device (10) of the shock on composite structure (12), it is special
Sign is that at least one acoustic module (14-1) is referred to as main acoustic module, including clock (38).
3. it is according to claim 2 for detecting the detection device (10) of the shock on composite structure (12), it is special
Sign is that the remote communication devices (26) of the main acoustic module (14-1) are configured to and the detection device (10)
Other acoustic module (14-2,14-3) communications.
4. a kind of airframe (12), including composite structural part (40), which is characterized in that the structure member
(40) equipped with the detection device (10) of shock according to any one of the preceding claims.
5. airframe (12) according to claim 4, which is characterized in that the acoustic module is fixed to the knot
The surface (42) of structure component (40).
6. airframe (12) according to claim 4, which is characterized in that the acoustic module (14,14-1,14-2,
It 14-3) is arranged in the structure member (40).
7. airframe (12) according to claim 4, which is characterized in that at least one acoustic module (14) is fixed
To the surface (42) of the structure member (40), and at least one acoustic module (14) is arranged on the structure member (40)
It is interior.
8. the airframe (12) according to any one of claim 4 to 7, which is characterized in that the structure member
(40) mainly extend along a dimension (D1), the detection device (10) only includes first fixed to the structure member (40)
Hold the second acoustic module of first acoustic module (14-1) of (44) and the second end (46) fixed to the structure member (40)
(14-2)。
9. the airframe (12) according to any one of claim 4 to 7, which is characterized in that the structure member
(40) mainly extend along two dimensions (D2, D3), the detection device (10) includes being fixed to the structure member (40) extremely
Few three acoustic modules (14-1,14-2,14-3), will be described at least three acoustic module (14-1,14-2,14-3)
The distance (L1, L2, L3) that acoustic module separates two-by-two is all different.
10. for detecting the detection method of the shock on composite material aircraft device structure member (40), the structure member (40)
Equipped with the detection device (10) according to the shock any one of Claim 1-3, which is characterized in that the detection side
Method implements the detection device (10) according to the following steps：
- by the communicator (26) of main acoustic module (14-1) to other acoustic module (14-2, the 14- of detection device (10)
3) radiated radio frequency signal (34), the radio frequency signals (34) include the acoustic module of the detection device
Shared when base；
- be recorded in the definite duration and pass through by the recording device (24) of each acoustic module (14-1,14-2,14-3)
The sound wave that the structure member (40) is propagated；
- by the communicator (26) will by each acoustic module (14-1,14-2,14-3) record sound wave be transferred to processing
Unit (30)；And
- the sound wave that is passed of analysis is to detect any shock being happened on the structure member (40).
11. the detection side according to claim 10 for being used to detect the shock on composite material aircraft device structure member (40)
Method, which is characterized in that the step of analyzing the sound wave being passed includes the shock that assessment is happened on the structure member (40)
The step of degree of danger.
12. the detection side according to claim 10 for being used to detect the shock on composite material aircraft device structure member (40)
Method, which is characterized in that the step of analyzing the sound wave being passed includes the shock that positioning is happened on the structure member (40)
Step.
13. it is used to detect on composite material aircraft device structure member (40) according to any one of claim 10 to 12
The detection method of shock, which is characterized in that the detection device (10) is implemented in the flight course of the aircraft.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1262207A FR2999715B1 (en) | 2012-12-18 | 2012-12-18 | DEVICE AND METHOD FOR DETECTING IMPACT ON A COMPOSITE MATERIAL STRUCTURE. |
| FR1262207 | 2012-12-18 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103868994A CN103868994A (en) | 2014-06-18 |
| CN103868994B true CN103868994B (en) | 2018-05-29 |
Family
ID=48128463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310700773.6A Active CN103868994B (en) | 2012-12-18 | 2013-12-18 | For detecting the detection device of the shock on composite structure and detection method |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US9470659B2 (en) |
| CN (1) | CN103868994B (en) |
| FR (1) | FR2999715B1 (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2493929B (en) * | 2011-08-22 | 2015-11-25 | Bae Systems Plc | Determining impact damage in a composite member by acoustic wave processing |
| EP3043322A1 (en) * | 2015-01-12 | 2016-07-13 | Airbus Operations GmbH | System and method for damage tracking and monitoring during ground handling of aircraft |
| US20160239921A1 (en) * | 2015-02-16 | 2016-08-18 | Autoclaims Direct Inc. | Apparatus and methods for estimating an extent of property damage |
| FR3035510B1 (en) | 2015-04-21 | 2018-10-26 | Airbus Group Sas | ACOUSTICAL MEANS FOR DETECTION, LOCATION AND AUTOMATIC EVALUATION OF IMPACTS SUBJECT TO A STRUCTURE |
| EP3159851B1 (en) | 2015-10-23 | 2024-02-14 | Safran Landing Systems UK Ltd | Aircraft health and usage monitoring system and triggering method |
| TWI682876B (en) | 2016-05-27 | 2020-01-21 | 日商日本電氣股份有限公司 | Inspection system, control device and control method |
| ES2928656T3 (en) * | 2016-09-26 | 2022-11-21 | Subaru Corp | Damage detection system and damage detection method |
| CN106596723A (en) * | 2017-01-09 | 2017-04-26 | 温州大学 | Acoustic detection method of structural mechanical parameters of multilayer composite material |
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| FR2999715B1 (en) | 2015-01-16 |
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| US20140165728A1 (en) | 2014-06-19 |
| US9470659B2 (en) | 2016-10-18 |
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